Missile



Sept 13, 1960 M. M. KAMlMoTo 2,952,207

MISSILE Filed June 30, 1952 2 Sheets-Sheet 1 INVENTOR. 34 M|CHAEL M.KAMIMOTO ATTORNEYS Sept. 13, 1960 M. M. KAMlMoTo MISSILE 2 Sheets-Sheet2 Filed June 30. 1952 m f M A L n E.

INVENTOR.

MICHAEL M. KAMEMOTO ATTORNEYS MISSHJE Michael M. Kamimoto, China Lake,Calif., assignor to the United States of America as represented by theSecretary of the Navy Filed June 30, 1952, Ser. No. 296,508

3 Claims. (Cl. 102-50) (Granted under Title 35, U.S. Code (1952), sec.266) The invention described herein may be manufactured and used by orfor the Government of the United States of America for governmentalpurposes without the payment of any royalties thereon or therefor.

This invention relates in general to missiles, and more particularly toimprovementsl in flight controls for rockets.

One of the objects of the invention is to provide an improved system forcontrolling the azimuthal and elevational directions of movement of amissile, and controlling roll thereof about its axis of movement.

Another object is to actuate the directional control surfaces of `themissile by the ambient fluid through which the missile moves.

Another object is to actuate the control surfaces of a rocket by rampressure produced by movement of the missile through air.

Another object is to provide a differential fluid pressure operateddiaphragm device for actuating a control surface.

Another object is to provide a plurality of pairs of differentialpressure operated diaphragm devices for actuating azimuthal andelevational control surfaces, and a gyroscope for controlling saidsurfaces to effect roll correction of the missile.

Other objects and many of the attendant advantages of this inventionwill be readily appreciated as the same becomes better understood byreference to the following detailed description when considered inconnection with the accompanying drawings wherein:

Fig. l is a fragmentary side elevation of a rocket to which `the subjectof the invention is applied;

Fig. 2 is a section taken on line 2 2, Fig. details being omitted;

Fig. 3 is a section taken on line 3 3, Fig. 4, and an enlarged sectiontaken on line 3 3, Fig. 2, portions being broken away;

Fig. 4 is a section taken on line 4-4, Fig. 3;

Fig. 5 is a section taken on line 5 5, Fig. 3;

Figs. 6 and 6A are sections taken on line 6 6, Fig. 3;

Fig. 7 is an enlarged section taken on line 7 7, Fig. l, a portion beingbroken away;

Fig. 8 is a section taken on line 8 8, Fig. 7;

Fig. 9 diagrammatically illustrates the control system;

Fig. 10 is a section taken on line 11-11, Fig. 11, portions being brokenaway;

Fig. 1l is -a section taken on line 11 11, Fig. 10;

Fig. 11A is a section taken on line 11A-11A, Fig. 1l, showing anotherposition of parts;

Fig. l2 is a section taken on line 12 12, Fig. l0; and

Fig. 13 is a section through a conduit and valve of Fig. 9;

Referring in detail to the drawing, and particularly Figs. l to 8,rocket 20, movable along its longitudinal axis A, is of any conventionalform, which embodies the subject of the invention. The rocket casing ortube 21 is provided with four air scoops 22, 22a, 22h, 22C, spacedequiangularly about its periphery. Fixed fins 23,

l, internal Patented Sept. i3, i950 23a, 23h, 23e yare carried by therocket rearwardly of the respective scoops and each carries a movableiin. Since the n scoops and lin actuators are all identical thedescription of one will serve for all. As best shown in Figs. 4 to 8, asheet of flexible material 19 is clampingly held between the side platesof fixed n 23 and between the side plates of movable n 24, this servingto permit swinging movement of iin 24 about axis 25, as best shown bythe dotted positions, Fig. 5. A pair of elongated hollow flexiblediaphragrns or bags 26, 27 are secured to the inner wall of tube 21 by aplate 28 and a pin 29 aixed thereto, pin 29 having a flange 30 engagingthe bottom wall of la recess 31 and adapted to rock in a transverseplane of the rocket, as bes-t shown in Figs. 6 and 6A The outer end 32of the pin is convex and seats within a socket 33 carried by the inneredge of fin 24. In Fig. 6, bags 26, 27 have the same internal rampressure and fin 24 is in the solid line position shown in Fig. 5, thatis, in alignment with the direction of ight of the rocket. In Fig. 6A, adifferential pressure exists in bags 26, 27, bag 26 being larger incross section than bag 27, which has tilted plate 28 and its attachedpin 29, swinging iin 24 to one of the dotted positions of Fig. 5. Itwill be apparent that when bag 2'7 expands and bag 26 contracts, iin 24will be moved to the other dotted line position of Fig. 5. The actualamount of angular movement will depend on the differential pressure inthe two bags. The front ends of both bags communicate with air scoop 22,and the rear ends are both closed, as best shown in Figs. 7 and 8. Apipe 34 communicates with the rear end of bag 27 and a similar pipe 35communicates with the rear end of bag 26. As diagrammatically shown inFig. 9, similar bags 26a, 27a actuate iin 24a; bags 26b, 27b actuate iin24h; and bags 26C, 27e actuate iin 24C.

As best shown in Figs. 9 and 13, pipes 34, 35b are connected to anormally closed solenoid operated valve V1, which, when opened, willbleed air from pipes 34, 35b through vent port P1. Pipes 35, 34h aresimilarly connected to valve V2 land port P2. Pipes 34a, 35C aresimilarly connected to valve V3 and port P3, and pipes 35a, 34al aresimilarly connected to valve P4 and port P1.

Assuming that the system -is provided with only the construction so fardescribed, .the operation is as follows: When valve V1 is open and valveV2 closed, air will bleed out through port P1, reducing the pressure inpipes 34, 35b thus etfecting a diiferential pressure -between bags 26,27 and 2612, 27h, respectively, thus swinging fins 24, 24h in the samedirection. As will be apparent, if valve V2 is open and valve V1 closed,these iins will be swung in the opposite direction. Similarly, when oneof valves V3, V4 is open and the other closed, fins 24a, 24e will swingin one direction or the other, depending upon which of these valves isopen. The solenoids may be controlled by any suitable intelligence whichdictates change of direction and signals a corrective control to thevalves. As will be apparent, one pair of opposite tins controlsazimuthal `direction of flight and the other pair controls elevationaldirection of flight.

Roll of the rocket about its axis or direction of flight is alsocontrolled by the iins just described by moving opposite pairs thereofin opposite directions. A rotor 37, of a gyroscope, 38, provided withbuckets 39, is mounted for rotation by shaft 40 in gimbal 41, the latterbeing rotatable labout axis 42 on pintles 43 rotatably supported by therocket. A pipe L1 communicates with pipe 34 and terminates in frame 44,delivering air to jet 45. Pipe L2 communicates with pipe 35 andterminates in frame 44, delivering air to jet 46. Before the gimbal hasprocessed, the ends of pipes L1, L2 are misaligned from the airreceiving ends of jets 45, 46, respectively, by the same amount, as bestshown in Fig. l2, so that there is equal ow of air to .both jets. Whenthe gimbal precesses, one

of the jets becomes more nearly aligned with its supply pipe and theother less aligned with its supply pipe, thus changing the relativerates of flow through lines L1 and L2. Pipe L3 communicates with pipe35h, and pipe L4 communicates with pipe 34h, thes'e pipes similarlyterminating in frame 44 and supplying air to jets 47, 48, respectively,which latter are misaligned with pipes L2, L4 in the same mannerdescribed for jets 45, 46. Assuming that valves V1 and V2 are closed andthe gyroscope precesses as shown in Fig. 11A, pipe L1 will become lessaligned with jet 45, and pipe L2 will become more nearly aligned withjet 46, and the pressure in pipe L1 will be greater than in pipe L2. Dueto the similar misalignment of pipes L3, L4 with jets 47, 48,respectively, the pressure in pipe L4 will be greater than in pipe L3.Bags 27 and 26h will then collapse 4and bags 26 and 27h expand, thusmoving fins 24, 24b in opposite directions, As will be apparent, if thegyroscope precesses in the opposite direction, the opposite movement offins 24, 24b will be opposite to that just described. The oppositedirection of movement of opposite pairs of fins will, as will beapparent, apply a corrective force opposing roll of the rocket. Theother pair of fins 24a, 24e are similarly co-ntrolled by the gyroscopethrough pipe L5, terminating in frame 44 above pipe L4, a'nd pipe L3,terminating above pipe L3, at one side of the gimbal, and pipes L7 andL3 terminating, respectively below pipes L2, L1, at the other side ofthe gimbal. It will be apparent, therefore, that when a roll correctionis required, fins 24 and 24b will move in opposite `directions and fins24a and 24C will also move in opposite directions, the roll correctionof the pairs being cumulative.

Assuming again that the pressure in pipes L1, L1 are greater,respectively, than in pipes L2, L3 (which would effect a rollcorrection) and valve V1 is now opened, the pressure differentialbetween pipes L1 and L3 will then become greater and the pressuredifferential between pipes L1 and L2 will become less. Fins 24, 24h,instead of being swung in opposite directions in equal angular amountswill now move so that fin 24b is swung a greater amount, and fin 24 alesser amount, thus retaining substantially the same roll correction asformerly, but now producing an azimuthal steering correction. As will beapparent, opening of valve V2 instead of valve V1 produces an oppositeeffect. Opening of valve V1 (or V2) does not affect the position towhich fins 24a, 24e have been previously moved by the gyroscope controland the net roll corection thus remains substantial as it formerly waswith an azimuthal steering correction added to the roll correction.Similarly, if valve V3 or V4 is opened while the fins are moved to aroll correction position, the net roll correction remains substantiallyas it formerly was with lan elevational correction added to the rollcorvrection.

Obviously many modifications and variations of the present invention arepossible in the light of the above teachings. It is therefore to beunderstood that within the scope of the appended claims the inventionmay be practiced otherwise than as specifically described.

What is claimed is:

l. Directional flight control and roll control apparatus for a missilecomprising; first and second vertical iins movably carried by themissile at substantially diametrically opposite sides thereof adapted tocontrol azimuthal direction of movement of the missile, third and fourthhorizontal fins movably carried by the -missile at substantiallydiametrically opposite sides thereof adapted to control elevationaldirection of movement of the missile, a

first pair offiexible expansible chambers operatively connected to thefirst fin adapted to move same in opposite directions from a normallyneutral position in response to gas pressure applied within saidchambers, second, third, and fourth pairs of similar chambers similarlyconnected, respectively, to said second, third and fourth fins adaptedto similarly move same, means for applying the same` gas pressure to allof said chambers when said fins are all in their neutral positions,first valve means for reducing the pressure in one chamber of the firstpair and one chamber of the second pair to effect differential pressurebetween the respective pairs and effect movement of the first .andsecond fins in one direction, second valve means for reducing thepressure in the other chamber of the first pair and the other chamber ofthe second pair to effect differential pressures in the respective pairsand effect movement of the first `and second fins in the oppositedirection, whereby said first and second valves control the azimuthaldirection of flight, third and fourth valves similarly Vconnecting thethird and fourth pairs of chambers for controlling the elevationaldirection of movement, `a gyroscope carried by the missile, and valvemeans operable in response to precession of the gyroscope for reducingthe pressure in said one chamber of the first pair of chambers and saidother chamber of the second pair, or reducing pressure in saidotherchamber of the first pair and said one chamber of said second pair,whereby said first and second fins move in opposite di'- rections andcorrect roll of the missile about its direction of movement, said lastnamed valve means being adapted to similarly control said third andfourth fins for also correcting roll. v

2. Apparatus in accordance with claim l including means for deliveringambient air under ram pressure to all of said chambers to apply said gaspressure therewithin.

3. Apparatus in accordance with claim 2 wherein said valve means isconstructed and arrangedto deliver air from at least some of saidchambers to said gyroscope for rotating its rotor.

References Cited in the file of thisl patent UNITED STATES PATENTS2,183,311 Goddard Dec. l2, 1939 2,322,782 Hemstreet June 29, 19432,414,898 Rons Jan. 28, 1947 2,419,443 Eaton Apr. 22, 1947 2,584,127Harcum et al. Feb. 5, 1952 FOREIGN PATENTS 579,816 Great Britain Aug.16, 1946

